Center Instrument Pedestal Display

ABSTRACT

According to one embodiment, a center pedestal display includes a plurality of mounting faces and a high-resolution screen. The plurality of mounting faces include a first mounting face that is substantially parallel with a first surface of a pedestal mounting block of an existing instrument pedestal and a second mounting face that is substantially parallel with a second surface of the pedestal mounting block, the second surface intersecting the first surface at an angle such that the first surface is not parallel to the second surface. The existing instrument pedestal includes one or more pedestal gauges and one or more pedestal switches. The high-resolution screen is configured to display information comprising at least some information provided by the one or more pedestal gauges. The high-resolution screen is approximately 6×8 inches and has a resolution of at least 1024×768 pixels.

RELATED APPLICATIONS

This application is a continuation-in-part of U.S. application Ser. No.12/366,451 filed Feb. 5, 2009 and entitled “Center Instrument PedestalDisplay,” which claims the benefit under 35 U.S.C. §119(e) of U.S.Provisional Application No. 61/194,891 filed Sep. 30, 2008, entitled“F-16 Center Pedestal Display Housing”.

TECHNICAL FIELD

This disclosure relates in general to aircraft instrumentation and moreparticularly to an aircraft center instrument pedestal display.

OVERVIEW

In some aircraft, such as F-16 fighter jets, F-15 fighter jets, A-10attack aircraft and F-22 fighter jets, a center instrument pedestalcomprises components such as instruments, gauges, and/or switches thatprovide information and functionality to a pilot. For example, thecomponents may comprise altimeters, airspeed indicators, directionalgyroscopes, vertical velocity indicators, navigation mode selectors, andfuel switches.

SUMMARY OF EXAMPLE EMBODIMENTS

In accordance with one embodiment of the present disclosure, a centerpedestal display includes a plurality of mounting faces, one or moredisplay switches, and a screen. The plurality of mounting faces includea first mounting face that is substantially parallel with a firstsurface of a pedestal mounting block of an existing instrument pedestaland a second mounting face that is substantially parallel with a secondsurface of the pedestal mounting block. The existing instrument pedestalincludes one or more pedestal gauges and one or more pedestal switches.The one or more display switches are located on the display andconfigured to provide one or more functions of the one or more pedestalswitches. The screen is configured to display information that includesat least some of the information provided by the one or more pedestalgauges.

Numerous technical advantages are provided according to variousembodiments of the present disclosure. In certain embodiments, a largedisplay may be provided to a pilot to provide situational awarenesscapabilities while losing little or none of the information provided byinstrumentation on the existing center pedestal housing.

Other technical advantages of the present disclosure will be readilyapparent to one skilled in the art from the following figures,descriptions, and claims. Moreover, while specific advantages have beenenumerated above, various embodiments may include all, some, or none ofthe enumerated advantages.

BRIEF DESCRIPTION OF THE DRAWINGS

For a more complete understanding of the present disclosure and itsadvantages, reference is now made to the following description, taken inconjunction with the accompanying drawings, in which:

FIG. 1 is a front view illustrating an example embodiment of a centerinstrument pedestal;

FIG. 2 is a front perspective view illustrating an example embodiment ofa mounting block having legacy components removed;

FIG. 3 is a front view illustrating an example embodiment of a mountingblock populated with new components;

FIG. 4 is a rear view of the example mounting block illustrated in FIG.3;

FIG. 5A is a front perspective view illustrating a housing of anembodiment of a processing canister module;

FIG. 5B is a rear perspective view illustrating a housing of anembodiment of a processing canister module;

FIG. 5C is a front perspective view illustrating internal components ofan embodiment of a processing canister module;

FIG. 5D is a top cross-section view illustrating an embodiment of aprocessing canister module;

FIG. 6A is a front perspective view illustrating a housing of anembodiment of a power distribution unit (PDU) canister module;

FIG. 6B is a rear perspective view illustrating a housing of anembodiment of a PDU canister module;

FIG. 6C is a front perspective view illustrating internal components ofan embodiment of a PDU canister module;

FIG. 6D is a side cross-section view illustrating an embodiment of a PDUcanister module;

FIG. 7A is a front perspective view illustrating an embodiment of adisplay interface; and

FIG. 7B is a rear perspective view illustrating an embodiment of adisplay interface.

DETAILED DESCRIPTION

In some aircraft, such as F-16 fighter jets, F-15 fighter jets, A-10attack aircraft and F-22 fighter jets, a center instrument pedestalcomprises components such as instruments, gauges, and/or switches thatprovide information and functionality to a pilot. Components may beremoved and installed in order to replace failed components, upgradeexisting capabilities, or add new capabilities. For example, analogcomponents may be upgraded to digital components. As another example,new components may be added to upgrade an aircraft's situationalawareness capabilities.

According to various embodiments, old components may be replaced withcanister modules that host new components. The new components, whencombined with a display, may provide a pilot with enhanced situationalawareness capabilities. For example, the display may comprise a screenthat may display navigational and routing maps. Embodiments of theenhanced display may provide graphic or digital read-outs of flightinformation and data processed by one or more canister modules.Additionally, embodiments of the display may provide video and improvedaccess to infrared capabilities. The canister module may be installed inan existing center pedestal without modifying the pedestal.

Embodiments of the present invention and its advantages are bestunderstood by referring to FIGS. 1 through 6B of the drawings, likenumerals being used for like and corresponding parts of the variousdrawings.

FIG. 1 illustrates an example of a front view of a center instrumentpedestal 10 for a standard F-16 aircraft. As illustrated, centerinstrument pedestal 10 comprises a mounting block 20 and components 30a-30 n. Components 30 may comprise navigation and other flightinstruments such as altimeters, airspeed indicators, directionalgyroscopes, vertical velocity indicators, navigation mode selectors, andfuel switches. As illustrated in FIG. 1, components 30 comprise legacycomponents. It should be understood, however, that components 30 ofmounting block 20 may be any type of components, such as new components,replacement components, legacy components, or a combination of any ofthe preceding. Replacement components may include components thatsubstitute for other components, such as a digital component that mayreplace an analog component, or components used to replace a failedcomponent, such as a component of the same type as the failed component.

FIG. 2 illustrates an example of a front view of mounting block 20. Asillustrated, mounting block 20 has a surface that defines a plurality ofpedestal apertures 22 a-22 b. As illustrated, pedestal apertures 22 a-22b may be defined by the surface of mounting block 20. In a standard F-16mounting block, the dimension of pedestal apertures 22 a may beapproximately 3.0 to 3.50 inches square. In some embodiments, the frontof mounting block 20 may face the cockpit of the aircraft and thus bereadily accessible to the pilot.

According to some embodiments, new instruments comprising one or morecomponents may be installed in mounting block 20. For example, acomponent may be installed in mounting block 20 through a pedestalaperture 22. In some embodiments, inserting the new component through apedestal aperture 22 may allow the aircraft to be upgraded from withinthe cockpit without modifying the structure of the aircraft. However,installing the new component through a pedestal aperture 22 and/orreusing mounting block 20 may restrict the size, shape, and/or number ofcomponents that may be installed. Additionally, the new component mayneed to be located in a particular position to align with and/or connectto legacy equipment of a fixed size in a fixed position within mountingblock 20.

FIG. 3 illustrates an example of a front view of a mounting block 20populated with components. Pedestal apertures 22 may be left unpopulatedor they may be populated with any suitable components. For example,pedestal aperture 22 a may be populated with a canister 60.

Canister 60 may generally provide a platform to host digital flightinstruments and/or enhanced processing capabilities for mission planningand/or control. Such flight instruments and/or processing capabilitiesmay provide feedback and/or situational awareness capabilities that mayor may not be offered by components 30. Accordingly, canister 60 mayprovide additional or different capabilities over legacy flightinstruments, while maintaining space and design parameters for anaircraft cockpit. Embodiments of canister 60 may be installed in theexisting center instrument pedestal without modifying the structure ofthe aircraft. Specifically, the dimensions of canister module 60 may besuch that canister 60 may fit through a pedestal aperture 22 of mountingblock 20. Thus, embodiments of canister 60 may permit an aircraft to beupgraded from within the cockpit. Additionally, embodiments of canister60 may be designed such that installing canister 60 does not alter theweight and/or center of gravity of a loaded center instrument pedestal.Canister 60 may also be designed using existing shock and vibrationrequirements for F-16 multi-function display (MFD).

In some embodiments, canisters 60 may be installed to provide certainfunctionality. For example, a particular canister 60 may provideprocessing capabilities and comprise a primary flight reference (PFR)unit or an image capture unit (ICU). As another example, a canister 60may function to provide power to a center instrument pedestal andcomprise a power distribution unit (PDU). As is described below, thesecanisters may vary in size from each other and may contain differentcomponents.

FIG. 4 illustrates a rear view of the example mounting block 20illustrated by FIG. 3. Although FIGS. 3 and 4 illustrate a particularembodiment that includes particular components that are each configuredto provide certain functionality, alternative embodiments may includeany appropriate combination of components with the describedfunctionality divided between the components in any suitable manner.

FIGS. 5A-5D illustrate an embodiment of a processing canister 100.Processing canister 100 may comprise a PFR unit or an ICU. FIGS. 5A-5Bare front and rear perspective views, respectively, illustrating ahousing for components of processing canister 100. FIG. 5C is a frontperspective view of example internal components of processing canister100. FIG. 5D is a side cross-section view illustrating various internalcomponents of processing canister 100. Although FIGS. 5A-5D illustrate aparticular embodiment of a processing canister 100 that includesparticular components that are each configured to provide certainfunctionality, alternative embodiments may include any appropriatecombination of components with the described functionality dividedbetween the components in any suitable manner.

Processing canister 100 may include any components to providecapabilities that may be supported by instruments 30. For example,processing canister 100 may include altimeters, directional gyroscopes,or air speed vertical velocity sensors. Embodiments of processingcanister 100 may include one or more digital (or analog) components.Additionally, embodiments of processing canister 100 may providefunctionality such as improved access to infrared sensing, navigationalmaps and routing information, and/or video.

With reference to FIGS. 5A-5B, the housing of processing canister 100may comprise a mounting plate 110 and a body 120. The housing ofprocessing canister 100 may generally function to support, provideinterface to, protect, and remove heat from internal components ofprocessing canister 100.

Mounting plate 110, in one embodiment, is used to mount processingcanister 100 to a mounting block. Mounting plate 110 may comprise one ormore holes 112 a-112 n, which may fit screws that mount processingcanister 100 to a mounting block, such as mounting block 20 of FIGS.1-4. Mounting plate 110 may also facilitate the proper alignment ofprocessing canister 100 such that front connector 116 is positioned tomate with a corresponding connector associated with a display interface.Mounting plate 110 may be marked to identify the correct pedestalaperture to insert the processing canister 100. For example, mountingplate 110 may comprise a diagram indicating the installation locationfor the processing canister 100.

Front connector 116 may connect internal components of processingcanister 100 to a display. For example, front connector 116 may matewith a corresponding connector of display interface 300 of FIGS. 7A-7B.Accordingly, front connector 116 may enable a visual or graphic read-outof flight data or other instrument measurements. In certain embodiments,front connector 116 may represent a male or female end of a parallelport, a USB port, or any other suitable port for transferring data orsignals of any type.

Body 120 may contain one or more internal components of processingmodule 100. Embodiments of body 120 may comprise heat sink side plates130 a-130 b, a top plate 140, a rear plate 150, and a bottom plate 160(illustrated in FIGS. 5C-5D). In some embodiments, body 120 may beapproximately 3.25″×3.25″×7.85.″ In other embodiments, the profile ofbody 120 may be between 3.15″ and 3.45″, and the length may be between6″ to 8″. Accordingly, body 120 may fit through a pedestal aperture 22in a mounting block 20. Thus, processing canister 100 may be used toretrofit an existing mounting block with expanded features orcapabilities.

Top plate 140 and bottom plate 160 may be substantially similar.Likewise, side plates 130 may be substantially similar to each other.The plates may be manufactured from any suitable material including, butnot limited to, a metal, a plastic, or a metal alloy. As illustrated,rear plate 150 may join side plates 130, top plate 140 and bottom plate160. Rear plate 150 may also position a rear connector 118 to align andmate with a suitable component of an aircraft. Rear connector 118 maygenerally represent an aircraft interface that is configured to coupleinternal components of processing canister 100 to any suitable aircraftcomponents and circuitry, such as an instrument in the aircraft.Mounting plate 110, side plates 130 a-130 b, top plate 140, rear plate150, and bottom plate 160 may be joined using any suitable fasteningmechanism, such as one or more screws 114.

In certain embodiments, side plates 130 comprise a heat sink.Specifically, side plates 130 a-130 b may absorb thermal energygenerated by one or more internal components of processing canister 100and transfer the absorbed thermal energy to a fluid such as ambient air.Combining structural and cooling functions in the housing of processingcanister 100 may conserve interior space for other components while alsoproviding a mechanism for dissipating thermal energy generated by theinterior components.

To facilitate the dissipation of thermal energy, embodiments of sideplates 130 a-130 b may be manufactured from a suitable thermal conductorsuch as, for example, copper or an aluminum alloy. Additionally, asillustrated, side plates 130 may comprise a plurality of fins 132. Fins132 may generally facilitate the transfer of absorbed thermal energyaway from side plates 130. The thickness and spacing of fins 132 may beoptimized to promote free or forced convection along the surface of sideplates 130.

In certain embodiments, each side plate 130 may further comprise a fan134. Fan 134 may assist in the dissipation of thermal energy byincreasing airflow over the surface of a side plate 130. Accordingly,fan 134 may maintain a larger temperature gradient over side plates 130by replacing warmer air more quickly than passive convection. Asillustrated, fan 134 may be within a cut out on the exterior portion ofa side plate 130. Accordingly, in certain embodiments, an upper surface(i.e., the surface from which air exits) of fan 134 may be below, orlevel with an outermost surface of side plate 130. Mounting a fan 134 toa side plate 130 in such a manner may improve the cooling of internalcomponents of a canister module while conserving interior space withinthe module for such components.

FIGS. 5C-5D illustrate various internal components of processingcanister 100. Internal components of processing canister may include aprocessor 170, a processor interface card (PIC) 172, a 1553 PCIMezzanine Card (PMC) 174, a PMC interface card 176, memory 180, and aelectromagnetic interference (EMI) gasket 190. The internal componentsof processing canister 100 may generally provide and support thefunctionality associated with processing canister 100. It should benoted that FIGS. 5C-5D are intended to illustrate example internalcomponents of a processing canister 100 and other embodiments mayinclude some, all, or none of the illustrated components.

Processor 170 may execute logic comprising commands and instructionsassociated with the services provided by processing canister module 100.Processor 170 may represent any suitable one or more devices capable ofprocessing and/or communicating electronic information. Examples ofprocessor 170 include, application-specific integrated circuits (ASICs),field-programmable gate arrays (FGPAs), digital signal processors(DSPs), and any other suitable specific or general purpose processors.In certain embodiments, processor 170 may comprise a single-boardcomputer (SBC) that comprises the components of a computer on a singlecircuit board. Processor 170 may also include an advanced technologyattachment (ATA) bus, a graphics controller, and multiple USB ports.

Processor 170 may interface with PIC 172. In operation, PIC 172 may sendand/or receive data and other information to and from processor 170. PIC172 may offer video buffering capabilities, provide a precision pressuretransducer interface, and/or control analog or digital discreteinterfaces. Embodiments of PIC 172 may include one or more RS-232 ports,one or more RS-422 ports, one or more (universal serial bus) USB ports,an Ethernet controller, a barometric setting circuit, and/or one or moreFGPAs.

In certain embodiments, processor 170 may be mounted directly to a sideplate 130. As previously described, side plate 130 may function as aheat sink. Accordingly, mounting processor 170 to a side plate 130 mayfacilitate the dissipation of thermal energy generated during operation.Additionally, embodiments of processor 170 may be designed to withstanda variety of environmental conditions. For example, processor 170 maywithstand 90% non-condensing humidity, temperatures from −40 to 55degrees Celsius and up to 10 G shock.

In operation, processor 170 may generate flight data. The generatedflight data may be based on one or more instrument readings generated byan aircraft component and received by processor 170 via rear connector118. Flight data includes, but is not limited to an airspeedmeasurement, a vertical velocity measurement, an altimeter measurement,an attitude indicator, a heading indicator, and a turn and bankindicator. Additionally, in certain embodiments, processor 170 mayreceive video data and/or infrared measurements from suitable aircraftcomponents and process each for display to a pilot.

PMC card 174 may be a single, dual or quad channel MIL-STD-1553 PMC cardor any other suitable data bus. MIL-STD-1553 is a military standard thatdefines both mechanical and electrical characteristics of a serial databus. Embodiments of PMC card 174 may be capable of simultaneouslysimulating a bus controller (BC), up to 31 remote terminals (RTs), andbus monitor (BM) functions including full error injection and detection.

PMC card 174 may be mounted to card mounts 179. Card mounts 179 maydissipate heat generated by PMC card 174 during operation by providing aspacing between PMC card 174 and one or more other internal components.Additionally, embodiments of PMC card 174 may also be able to operate intemperatures ranging from −40 to 85 degrees Celsius and up to 95%non-condensing humidity.

PMC interface card 176 may provide an intelligent interface between PMCcard 174 and processor 170. Embodiments of PMC interface card 176 cardmay function as a bus controller (BC), a remote terminal (RT), a busmonitor (BM) or a remote terminal/bus monitor (RT/M). In someembodiments, PMC interface card 176 may comprise a four connector PCIinterface, a PCI bus and/or a plurality of A/D channels for (directionmanagement system/target management system) DMS/TMS.

Memory 180 may store any data or logic used by processor 170 to providefunctionality for processing canister 100. In particular, embodiments ofmemory 180 may store software and/or code for execution by processor170. Memory 180 may comprise any form of volatile or non-volatile memoryincluding, without limitation, a solid state drive (SSD), magneticmedia, optical media, random access memory (RAM), dynamic random accessmemory (DRAM), flash memory, removable media, or any other suitablelocal or remote component.

As illustrated in FIG. 5D, processor 170, PIC 172, PMC card 174, and PMCinterface card 176 may be stacked together by card mounts 178 a-178 n.The stack may be generally referred to as a processing card assembly. Insome embodiments, the processing card assembly may also comprise memory180. Card mounts 178 may also fasten and properly position each of thesecomponents, or one or more other devices, to a side plate 130. Invarious embodiments, card mounts 178 may uniformly separate eachcomponent with a spacing of approximately 0.5″.

EMI gasket 190 may line the perimeter of top plate 140 and bottom plate160. When processing canister 100 is positioned in a mounting block,such as mounting block 20 of FIG. 1, EMI gasket 190 may shieldelectrical components within the canister from electromagneticinterference generated by one or more adjacent canister modules. EMIgasket 190 may also prevent or eliminate the permeation of anyelectromagnetic interference generated by one or more components ofprocessing canister 100.

While the illustrated embodiment of processing canister 100 includes aparticular number and configuration of components, processing canister100 any components which operable to provide the recited functionality.Moreover, processing canister 100 may also include additional componentssuch as a video card or. an Internet card. Accordingly, embodiments ofprocessing canister 100 may include more, fewer, or other components.

FIGS. 6A-6D illustrate an embodiment of a PDU canister module (“PDUcanister”) 200. FIGS. 6A-6B are front and rear perspective views,respectively, illustrating a housing for components of PDU canister 200.FIG. 6C is a front perspective view of internal components of PDUcanister 200. FIG. 6D is a side cross-section view illustrating variousinternal components of PDU canister 200. Although FIGS. 6A-6D illustratea particular embodiment of a PDU canister 200 that includes particularcomponents that are each configured to provide certain functionality,alternative embodiments may include any appropriate combination ofcomponents with the described functionality divided between thecomponents in any suitable manner.

With reference to FIGS. 6A-6B, the housing of PDU canister 200 maycomprise a mounting plate 210 and a body 220. The housing of PDUcanister 200 may generally function to support and protect internalcomponents of PDU canister 200.

Mounting plate 210 may comprise one or more holes 212 a-212 n, which mayfit screws that mount PDU canister 200 to a mounting block, such asmounting block 20 of FIGS. 1-4. In addition to mounting PDU canister 200to a mounting block, mounting plate 210 may also ensure the properalignment of PDU canister 200 within the mounting block.

Body 220 generally comprises side plates 230 a-230 b, a top plate 240, arear plate 250, and a bottom plate 260 (illustrated in FIGS. 6C-6D). Insome embodiments, body 220 may be approximately 3.25″×3.25″×9.″ Inparticular embodiments, the profile of body 220 may be between 3.15″ and3.45″, and the length may be between 6″ to 8″. Accordingly, body 220 mayfit through a pedestal aperture 22 in a mounting block 20.

Side plates 230, top plate 240, rear plate 250, and bottom plate 260 maybe substantially similar to side plates 130, top plate 140, rear plate150, and bottom plate 160 of processing module 100 illustrated in FIGS.5A-5D. These components may be connected using one or more screws 214.

In the illustrated embodiment, side plates 230 do not include a fan.However, it should be noted that embodiments of side plates 230 mayinclude one or more fans such as fan 134 described with respect tocanister module 100. Additionally, embodiments of side plates 230, topplate 240, rear plate 250, and bottom plate 260 may vary in size fromside plates 130, top plate 140, rear plate 150, and bottom plate 160 ofcanister module 100.

PDU module 200 may also comprise a rear connector 218. Rear connector218 may interface with aircraft components and circuitry. Embodiments ofrear connector 218 may be substantially similar to rear connector 118 ofprocessing module 100.

Referring now to FIGS. 6C-6D, various internal components of anembodiment of PDU module 200 are illustrated. As discussed above,embodiments of PDU module 200 may provide power to components of acenter pedestal display, such as one or more processing modules 100.Accordingly, PDU module 200 may comprise a plurality of power modules280 and a plurality of capacitors 282. Power modules 280 may be anysuitable power generating device, such as one manufactured by Vicor®. Inoperation, power modules 280 may generate power that is stored bycapacitors 282. In one embodiment, one or more power modules 280 may beused to condition and filter the incoming aircraft power.

As illustrated, power modules 280 may line side plates 230. Duringoperation, power modules 280 may generate thermal energy. Similar toside plates 130 of processing canister 100, side plates 230 may alsofunction as heat sinks. Accordingly, mounting power modules to sideplate 230 facilitate the dissipation of thermal energy away from powermodules 280. Thus, embodiments side plates 230 may offer both structuraland cooling functions.

PDU module 200 may also comprise an EMI gasket 290. Similar to EMIgasket 190 of processing module 100, EMI gasket 290 may shieldelectrical components within the canister from electromagneticinterference generated by one or more adjacent components. EMI gasket290 may also prevent or eliminate the permeation of any electromagneticinterference generated by one or more components of PDU canister 200.

FIGS. 7A-7B illustrate an embodiment of a display interface 300 that maybe fitted to an existing center instrument pedestal. FIG. 7A is a topperspective view of display interface 300 positioned over mounting block20. FIG. 7B is a bottom perspective view of display interface 300illustrating connectors 330 a-n that may mate with correspondingconnectors associated with one or more processing canisters 100 or PDUcanisters 200.

Embodiments of display interface 300 may be sized and shaped so as tofit on mounting block 20 without interfering with other functions andcapabilities needed by a pilot. In various embodiments, displayinterface 300 may comprise a plurality of mounting faces 352 a-352 b.Each mounting face may be configured such that it is substantiallyparallel to a corresponding surface on a face 24 of mounting block 20.In some embodiments, display interface 300 may mate to a display mount350 via a plurality of fasteners 342, which may secure display interface300 to display mount 350. In such embodiments, the display mount 350 maybe installed on the mounting block of the center instrument pedestal anddisplay interface 300 may be mounted to display mount 350. It should benoted that the size and shape of display interface 300 may generally besuch that it does not interfere with a pilot climbing in and out of anaircraft cockpit.

Display interface 300 may comprise appropriate hardware and/or softwareto provide a pilot with situational awareness capabilities. For example,display interface 300 may comprise a screen 310, which may displayinformation and capabilities to a pilot. Embodiments of screen 310 mayprovide a digital display of some or all of the information andcapabilities provided by components 30 of FIG. 1. In some embodiments,screen 310 comprise a graphical user interface (GUI) with a touch-screeninterface for pilot instrument control. In certain embodiments, thedisplay mode or other settings for screen 310 may be adjusted using acontroller that is positioned on the throttle and/or stick of theaircraft.

Embodiments of display interface 300 may provide a pilot display that islarger than standard pilot displays, such as F-16 displays.Specifically, in some embodiments, screen 310 may provide a 10.4″display in an area normally expected to house an 8.4″ screen withoutprotruding beyond the width of an existing center pedestal. Providing alarger screen 310 may permit embodiments of display interface 300 toprovide enhanced situational awareness capabilities. For example, screen310 may display larger and more detailed route and guidance maps than atraditional screen.

In some embodiments, screen 310 may be a high-resolution screen. Forexample, certain embodiments of screen 310 may include high-resolutionglass that is approximately 6×8 inches and provides a resolution ofapproximately 1624×76.8 pixels. In other embodiments, screen 310 mayinclude high-resolution glass that is approximately 5×7 inches andprovides a resolution of approximately 800×600 pixels. In otherembodiments, screen 310 may be other sizes (e.g., other 4:3 ratios, 16:9ratios, or any other ratio) and may include high-resolution glass thatprovides a resolution greater than 1024×768 pixels, including, but notlimited to, 1152×864 pixels, 1280×720 pixels, 1280×960 pixels, 1280×1024pixels, 1440×900 pixels, 1600×1200 pixels, 1680×1050 pixels, 1920×1080pixels, 1920×1200 pixels, and the like.

Some embodiments of display interface 300 also comprises a plurality ofswitches 320 a-320 n. Switches 320 may provide any suitablefunctionality for a center instrument pedestal, such as functionalityassociated with existing switches. For example, switches 320 maycomprise one or more fuel switches or navigational mode selectors. Invarious embodiments, switches 320 may be positioned on a common side ofdisplay interface 300. Positioning such components on a common side ofdisplay interface 300 may generally allow screen 310 to comprise alarger area than otherwise because only one dimension of screen 310 isconstrained. Accordingly, as illustrated in FIG. 7A, screen 310 mayoverlap one or more pedestal apertures 22 of mounting block 20 where oneor more legacy switches were previously installed.

Embodiments of display interface may also comprise one or more USB ports322. USB port 322 may enable a pilot to download mission data to displayinterface 300. USB port 322 may also enable a pilot to upload missiondata from display interface 300. In some embodiments, USB port 322 mayallow for one or more other instruments to interface with displayinterface 300. In some embodiments, display interface 300 mayadditionally or alternatively include one or more Ethernet ports. Forexample, in certain embodiments, USB port 322 may be replaced with anEthernet port 322. Ethernet port 322 may allow for the samefunctionality as USB port 322 described above.

Embodiments of display interface 300 may also comprise one or more bezelkeys 325. For example, display interface 300 may include bezel keys 325around the perimeter of screen 310. In certain embodiments, displayinterface 300 may include bezel keys 325 at the top and/or bottom ofscreen 310. In certain embodiments, display interface 300 may includebezel keys 325 to the left and/or right of screen 310. Bezel keys 325may provide any suitable functionality for a center instrument pedestal,including, but not limited to, allowing a pilot to select itemsdisplayed on screen 310 proximate to bezel keys 325.

Referring to FIG. 7B, display interface 300 may also comprise aplurality of connectors 330. Each connectors 330 may comprise a blindmate connector that mates with a front connector 116 of a processingcanister 100. In this manner, display interface 300 may receive flightdata recorded and/or generated by a processing canister 100. In someembodiments, the received data may be pre-processed by a processingcanister 100 such that the received data is ready for display on screen310. In alternative embodiments, the received data may be processed bydisplay interface 300 for display on screen 310.

Some embodiments of display interface 310 may comprise one or morecooling fans 340. Cooling fan 340 may be installed in display interfacein lieu of a connector 330. Cooling fan may draw heat away fromcomponents of display interface 300.

Although FIGS. 7A-7B illustrate a particular embodiment of a displayinterface 300 that includes a particular number and arrangement ofcomponents configured to provide certain functionality, alternativeembodiments may include any appropriate combination of components withthe described functionality divided between the components in anysuitable manner. Additionally, embodiments of display interface mayinclude more, fewer, or other components.

While the present invention has been described in detail with referenceto particular embodiments, numerous changes, substitutions, variations,alterations and modifications may be ascertained by those skilled in theart, and it is intended that the present invention encompass all suchchanges, substitutions, variations, alterations and modifications asfalling within the spirit and scope of the appended claims.

1. A center pedestal display for an aircraft, comprising: a plurality ofmounting faces, comprising: a first mounting face that is substantiallyparallel with a first surface of a pedestal mounting block of anexisting instrument pedestal, the existing instrument pedestalcomprising one or more pedestal gauges and one or more pedestalswitches; and a second mounting face that is substantially parallel witha second surface of the pedestal mounting block, the second surfaceintersecting the first surface at an angle such that the first surfaceis not parallel to the second surface; a high-resolution screenconfigured to display information, the information comprising at leastsome information provided by the one or more pedestal gauges, thehigh-resolution screen being approximately 6×8 inches and having aresolution of at least 1024×768 pixels.
 2. The center pedestal displayof claim 1, further comprising one or more display switches located onthe display and configured to provide one or more functions of the oneor more pedestal switches.
 3. The center pedestal display of claim 2,wherein one of the one or more display switches comprises a fuel switch.4. The center pedestal display of claim 1, wherein the high-resolutionscreen is further configured to display information to a pilot that isfrom a source other than the one or more pedestal gauges.
 5. The centerpedestal display of claim 1, further comprising one or more USB ports.6. The center pedestal display of claim 1, further comprising one ormore bezel keys disposed around the high-resolution screen.
 7. Thecenter pedestal display of claim 1, further comprising one or moreconnectors, the one or more connectors configured to mate with acorresponding connector associated with a processing canister, theprocessing canister comprising one or more flight instruments.
 8. Thecenter pedestal display of claim 1, further comprising one or moreconnectors, the one or more connectors configured to receive flight datagenerated by a processing canister.
 9. The center pedestal display ofclaim 1, wherein the high-resolution screen is configured to displayflight data generated by a processing canister.
 10. The center pedestaldisplay of claim 1, further comprising a plurality of fasteners, thefasteners configured to mount the display to a display mount, thedisplay mount affixed to the center pedestal mounting block.
 11. Thecenter pedestal display of claim 1, wherein the display is configuredto: receive an instruction from a controller positioned on the throttleof the aircraft; and change the displayed information in response to theinstruction.
 12. The center pedestal display of claim 1, wherein thedisplay is configured to: receive an instruction from a controllerpositioned on the stick of the aircraft; and change the displayedinformation in response to the instruction.
 13. The center pedestaldisplay of claim 1, further comprising one or more Ethernet ports. 14.The center pedestal display of claim 1, wherein the aircraft is an F-16.15. A center pedestal display for an F-16 aircraft, comprising: ahigh-resolution screen configured to display information to a pilot, theinformation comprising at least some information provided by one or morepedestal gauges, the high-resolution screen being approximately 6×8inches and having a resolution of at least 1024×768 pixels; one or morebezel keys disposed around the high-resolution screen; and one or moredisplay switches configured to provide one or more functions of one ormore pedestal switches.
 16. The center pedestal display of claim 15,wherein the one or more display switches are disposed below the one ormore bezel keys.
 17. The center pedestal display of claim 15, whereinone of the one or more display switches comprises a fuel switch.
 18. Thecenter pedestal display of claim 15, further comprising one or moreEthernet ports.
 19. The center pedestal display of claim 15, furthercomprising one or more USB ports.
 20. A center pedestal display for anF-16 aircraft, comprising: a high-resolution screen configured todisplay information to a pilot, the information comprising at least someinformation provided by one or more pedestal gauges, the high-resolutionscreen being approximately 6×8 inches and having a resolution of atleast 1024×768 pixels; one or more bezel keys disposed around theperimeter of the high-resolution screen; one or more display switchesconfigured to provide one or more functions of one or more pedestalswitches, the one or more display switches being disposed below the oneor more bezel keys; and one or more Ethernet ports.
 21. A centerpedestal display for an aircraft, comprising: a plurality of mountingfaces, comprising: a first mounting face that is substantially parallelwith a first surface of a pedestal mounting block of an existinginstrument pedestal, the existing instrument pedestal comprising one ormore pedestal gauges and a plurality of pedestal switches; and a secondmounting face that is substantially parallel with a second surface ofthe pedestal mounting block, the second surface intersecting the firstsurface at an angle such that the first surface is not parallel to thesecond surface; a plurality of display switches located on the displayand configured to provide one or more functions of the plurality ofpedestal switches; and a screen of the display configured to displayinformation, the information comprising at least some of the informationprovided by the one or more pedestal gauges.
 22. The center pedestaldisplay of claim 21, further comprising one or more Ethernet ports. 23.The center pedestal display of claim 21, wherein the aircraft is anF-16.
 24. The center pedestal display of claim 21, further comprisingone or more bezel keys disposed around the screen.